Hostname: page-component-cd9895bd7-mkpzs Total loading time: 0 Render date: 2024-12-25T06:14:30.560Z Has data issue: false hasContentIssue false
  • English
  • Français

Buckling of 45° Eccentric-Stiffened Waffle Cylinders

Published online by Cambridge University Press:  04 July 2016

R. R. Meyer
R. R. Meyer*
Affiliation:
Douglas Aircraft Company, Inc, California
Get access Rights & Permissions [Opens in a new window]

Extract

The cylindrical tankage which forms part of the primary structure of missiles and space vehicles may be subjected to high compressive axial and bending loads. Since allowable compressive stresses for monocoque construction are generally low because of small bending rigidity and sensitivity to geometric imperfection, it is advantageous to use some type of wall stiffening. One such choice is the integrally milled-out 45° waffle. This consists of a square gridwork of ribs which form 45° helices over the cylindrical surface. The panel is generally milled out in the flat and then bent up to form a circular cylinder. An advantage of the 45° construction is the exclusion of buckling modes between hoop reinforcement; such modes are frequently critical for the 0° to 90° type of stiffening.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 679 , July 1967 , pp. 516 - 520
Copyright
Copyright © Royal Aeronautical Society 1967

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1.Wang. Applied Elasticity, pp 341, 350. McGraw-Hill. 1953.Google Scholar
2.Thielemann, W. F.New Developments in the Nonlinear Theories of the Buckling of Thin Cylindrical Shells. Aeronautics and Astronautics, edited by Hoff, and Vincenti, , pp 99–102. Pergamon. 1960.Google Scholar
3.Vlasov, V. Z. General Theory of Shells and its Applications in Engineering. NASA TT F-99, pp 521-532, April 1964.Google Scholar
4. Mushtari and Galimov. Non-Linear Theory of Thin Elastic Shells. NASA TT F-62, pp 304-313, 1961.Google Scholar
5.Seide and Weingarten. On the Buckling of Circular Cylindrical Shells Under Pure Bending. Journal of Applied Mechanics, pp 112–116, March 1961.Google Scholar
6. Horton and Cox. The Stability of Thin Walled Un-stiffened Circular Cylindrical Shells Under Nonuniformly Distributed Axial Load. Department of Aeronautics and Astronautics, Stanford University, 1965.Google Scholar